Cooling structure of turbine airfoil

• US 9,133,717 B2
• Filed: 01/08/2009
• Issued: 09/15/2015
• Est. Priority Date: 01/08/2008
• Status: Active Grant

• Current Assignee: IHI Corporation, Japan Aerospace Exploration Agency
• Original Assignee: IHI Corporation, Japan Aerospace Exploration Agency
• Inventors: Nakamata, Chiyuki, Yamane, Takashi, Fukuyama, Yoshitaka, Bamba, Takahiro
• Primary Examiner(s): YOUNGER, SEAN JERRARD
• Application Number:
  US12/812,227
• Publication Number:
  US 20110027102A1
• Time in Patent Office: 2,441 Days
• Field of Search: 415/115, 415/116, 415/175, 415/178, 416/90.R, 416/92, 416/97.R, 416/224, 416/231.R
• US Class Current: 1/1
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F05D 2240/121 related to the leading edge of a stator vane
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/303 related to the leading edge of a rotor blade
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/205 Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
• CPC Class Codes: F05D 2260/2212 by creating turbulence
• CPC Class Codes: F05D 2260/2214 by increasing the heat transfer surface
• CPC Class Codes: F05D 2260/22141 using fins or ribs

Abstract

A cooling structure of a turbine airfoil cools a turbine airfoil (10) exposed to hot gas (1), using cooling air (2) of a temperature lower than that of the hot gas. The turbine airfoil (10) includes an external surface (11), an internal surface (12) opposite to the external surface, a plurality of film-cooling holes (13) blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections (14) integrally formed with the internal surface and protruding inwardly from the internal surface. The turbine airfoil further includes a hollow cylindrical insert (20) which is positioned inside the internal surface of the turbine airfoil and to which the cooling air is supplied. The insert has a plurality of impingement holes (21) for impingement-cooling the internal surface (12).

Claims

1. A cooling structure of a turbine airfoil which cools a turbine airfoil exposed to hot gas using cooling air of a temperature lower than that of the hot gas,

the turbine airfoil comprising an external surface exposed to the hot gas, an internal surface opposite to the external surface and cooled by the cooling air, a plurality of film-cooling holes extending between the internal surface and the external surface and blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections integrally formed with the internal surface and protruding inwardly from the internal surface,

wherein a hollow cylindrical insert is set inside the internal surface of the turbine airfoil, the cooling air is supplied to an inside of the insert, and the insert has a plurality of impingement holes for impingement-cooling the internal surface,

wherein the plurality of heat-transfer promoting projections is set to be slightly shorter than a spacing between the internal surface of the turbine airfoil and the external surface of the insert, and wherein the heat-transfer promoting projections are formed in a cylindrical shape;

the film-cooling holes and the impingement holes are aligned to each other along the flow of the hot gas, the film-cooling holes are arranged at a pitch P2 along the flow of the hot gas, the impingement holes are arranged at a pitch P1 along the flow of the hot gas so as to be positioned midway between the film-cooling holes which are adjacent to each other along the flow of the hot gas; and

the film-cooling holes and the impingement holes are arranged at a same pitch Py in a direction perpendicular to the flow of the hot gas, and the heat-transfer promoting projections are positioned at a position deviated from the film-cooling holes and the impingement holes in a direction perpendicular to the flow of the hot gas.

2. The cooling structure of the turbine airfoil as claimed in claim 1, wherein the heat-transfer promoting projections are formed in a cylindrical shape with rounded edge.

3. The cooling structure of the turbine airfoil as claimed in claim 1, wherein the heat-transfer promoting projections are arranged at positions which do not interfere with a flow path formed to cause flow from the impingement hole to the film-cooling hole adjacent to the impingement hole, at a desired pitch P3 along the flow of the hot gas.

4. The cooling structure of the turbine airfoil as claimed in claim 1,

wherein the pitch P2 of the film-cooling holes is 1 to 2 times as large as the pitch P1 of the impingement holes, and

the heat-transfer promoting projections have a pitch P3 equal to or smaller than half of the pitch P1 of the impingement holes, and the heat-transfer promoting projections are positioned at positions deviated from the impingement holes along the flow of the hot gas by half of the pitch P3.

5. The cooling structure of the turbine airfoil as claimed in claim 1, wherein the heat-transfer promoting projections are positioned at a position deviated from the film-cooling holes and the impingement holes at half of a pitch Py in a direction perpendicular to the flow of the hot gas, and further wherein the heat-transfer promoting projections are positioned at a position deviated from the film-cooling holes and the impingement holes at half of a pitch Px in a direction parallel to the flow of the hot gas.